Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan

1. A bypass turbine engine, wherein air flows circulate from upstream to downstream, the turbine engine extending axially and comprising:

an inner casing,

an inter-duct casing, and

an outer casing,

wherein a primary duct is defined between the inter-duct casing and the inner casing,

wherein a secondary duct is defined between the inter-duct casing and the outer casing,

wherein a rotary shaft comprises, at an upstream end, a movable fan comprising radial blades of which the free ends face the outer casing of the turbine engine so as to compress an air flow at least in the secondary duct, said radial blades of the movable fan extending in a same transversal plane with respect to an axis of the turbine engine,

wherein a plurality of variable-pitch radial stator vanes are mounted upstream of the movable fan, said variable-pitch radial stator vanes being configured to deflect incident axial air,

wherein the movable fan is configured to axially rectify said air deflected in the secondary duct, and

the turbine engine not being provided with stator vanes in contact with the outer casing downstream of the movable fan.

2. The turbine engine according to claim 1 , wherein the inner casing, the inter-duct and the outer casing are at a radial distance from one another in the turbine engine so as to define a turbine engine having a bypass ratio (BPR) that is at least equal to 15.

3. The turbine engine according to claim 1 , wherein a rotational speed of the free ends of the blades of the movable fan is less than 340 m/s.

4. The turbine engine according to claim 1 , wherein the plurality of variable-pitch radial stator vanes extends in a same plane which is transverse to an axis of the turbine engine.

5. The turbine engine according to claim 1 , wherein an axial distance between the plurality of variable-pitch radial stator vanes and the movable fan is between 0.1 and 10 times a mean chord of a variable-pitch radial stator vane.

6. The turbine engine according to claim 1 , wherein the blades of the movable fan extend between the inner casing and the outer casing of the turbine engine.

7. The turbine engine according to claim 1 , wherein each variable-pitch radial vane has an aerodynamic profile so as to accelerate a flow of the incident axial air in accordance with a laminar flow.

8. The turbine engine according to claim 1 , wherein each variable-pitch radial stator vane has a body which is movable in rotation about a radial axis.

9. The turbine engine according to claim 1 , wherein each variable-pitch radial vane has a fixed body and a movable flap.

10. The turbine engine according to claim 1 , wherein the plurality of variable-pitch radial stator vanes forms a planar transverse surface with respect to the axis of the turbine engine at a given pitch position of each of the variable-pitch radial stator vanes.

11. The turbine engine according to claim 1 , wherein the variable-pitch radial stator vanes are mounted on a fixed axial cone connected to the inner casing.

12. The turbine engine according to claim 1 , wherein the variable-pitch radial stator vanes extend radially between the inter-duct casing and the outer casing.

13. A bypass turbine engine, wherein air flows circulate from upstream to downstream, the turbine engine extending axially and comprising:

an inner casing,

an inter-duct casing, and

an outer casing,

wherein a primary duct is defined between the inter-duct casing and the inner casing,

wherein a secondary duct is defined between the inter-duct casing and the outer casing,

wherein a rotary shaft comprises, at an upstream end, a movable fan comprising radial blades of which the free ends face the outer casing of the turbine engine so as to compress an air flow at least in the secondary duct,

wherein a plurality of variable-pitch radial stator vanes are mounted upstream of the movable fan, said variable-pitch radial stator vanes being configured to deflect incident axial air,

wherein the movable fan is configured to axially rectify said air deflected in the secondary duct, and

the turbine engine not being provided with stator vanes in contact with the outer casing downstream of the movable fan and axially between radial blades of the movable fan.

14. A bypass turbine engine, wherein air flows circulate from upstream to downstream, the turbine engine extending axially and comprising:

an inner casing,

an inter-duct casing, and

an outer casing,

wherein a primary duct is defined between the inter-duct casing and the inner casing,

wherein a secondary duct is defined between the inter-duct casing and the outer casing,

wherein a rotary shaft comprises, at an upstream end, a movable fan comprising radial blades of which the free ends face the outer casing of the turbine engine so as to compress an air flow at least in the secondary duct,

wherein a plurality of variable-pitch radial stator vanes are mounted upstream of the movable fan, said variable-pitch radial stator vanes being configured to deflect incident axial air,

wherein the movable fan is configured to axially rectify said air deflected in the secondary duct,

wherein the turbine engine is not provided with stator vanes in contact with the outer casing downstream of the movable fan, and

wherein the inner casing, the inter-duct and the outer casing are at a radial distance from one another in the turbine engine so as to define a turbine engine having a bypass ratio (BPR) that is at least equal to 15.